微型涡流发生器对超临界翼型升阻特性影响实验研究

张进; 余春锦; 张彬乾

doi:10.13433/j.cnki.1003-8728.2016.0927

微型涡流发生器对超临界翼型升阻特性影响实验研究

doi: 10.13433/j.cnki.1003-8728.2016.0927

1.
南昌航空大学飞行器工程学院, 南昌 330036;
2.
西北工业大学航空学院, 西安 710072

详细信息

作者简介:
张进(1976-),讲师,硕士研究生,研究方向为流动控制和飞行器气动布局设计,zhangjin_nchu@163.com

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- 文章访问数: 111
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- 被引次数: 0
出版历程
- 收稿日期: 2014-01-14
- 刊出日期: 2016-09-05

Experimental Study of Micro Vortex Generator Effects on Lift-drag Characteristics of a Supercritical Airfoil

1.
School of Aircraft Engineering Nanchang Hangkong University, Nanchang 330063, China;
2.
School of Aeronautics Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 采用低速风洞实验方法，研究了安装在超临界翼型上的微型涡流发生器四种高度和安装位置对绕该翼型的流动影响。对比干净翼型和安装微型涡流发生器的翼型升阻特性，结果表明：同向安装的微型涡流发生器能减小阻力，但对升力和失速迎角影响不大；大尺寸微型涡流发生器减阻没有小尺寸效果好；高度低于0.4δ（δ为边界层名义厚度）的微型涡流发生器最佳安装位置为参考分离位置下游3.5δ~4.5δ处。
- 微型涡流发生器 /
- 超临界翼型 /
- 升阻特性 /
- 失速迎角
Abstract: This paper investigates the effect of Micro Vortex Generators (MVGs) on the supercritical airfoil aerodynamics using the wind tunnel. The results indicated that when installed co-rotating MVGs, the drag coefficient was decreased, and the lift and stall angle of attack changed little. The drag decreased more when the size of MVGs was smaller. As the height of MVGs was below 0.4 δ(δ is the velocity boundary-layer thickness), the optimal location was about 3.5δ~4.5δ downstream from the baseline separation point.
- micro vortex generator /
- airfoils /
- aerodynamics /
- drag coefficient

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参考文献(18)

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